Burner and method for reducing combustion humming during operation
First Claim
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1. A gas turbine burner, comprising:
- a flow duct, configured as an annular duct, adapted to guide a flow of one of combustion air and a combustion air/fuel mixture wherein the flow duct includes a swirl device for imposing a swirl on the flow, the swirl device being configured for the imposition of a swirl, which is non-uniform around the periphery of the annular duct, on the flow.
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Abstract
Combustion air or a combustion air/fuel mixture is supplied in a flow to a combustion process of a burner. A swirl, which is non-uniform in the peripheral direction, is imposed on the flow. A flow duct, in which is arranged a swirl device for imposing the swirl, is used for the supply of the combustion air or the combustion air/fuel mixture. As such, combustion oxcillations are reduced.
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Citations
11 Claims
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1. A gas turbine burner, comprising:
a flow duct, configured as an annular duct, adapted to guide a flow of one of combustion air and a combustion air/fuel mixture wherein the flow duct includes a swirl device for imposing a swirl on the flow, the swirl device being configured for the imposition of a swirl, which is non-uniform around the periphery of the annular duct, on the flow. - View Dependent Claims (2, 3, 4, 5, 8, 9, 10, 11)
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6. A method of reducing combustion oscillations during the operation of a gas turbine burner with a flow duct, configured as an annular duct, comprising:
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imposing a swirl, which is non-uniform around the periphery of the annular duct, on a flow, in the annular duct, of one of a combustion air/fuel mixture and of combustion air; and
supplying the flow to a combustion process. - View Dependent Claims (7)
feeding the fuel into the annular duct, by means of a fuel inlet, upstream of an outlet end of a swirl device arranged in the annular duct.
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Specification